EP1225322B1 - Apparatus to centre a tube in a turbine shaft - Google Patents

Apparatus to centre a tube in a turbine shaft Download PDF

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Publication number
EP1225322B1
EP1225322B1 EP01403059A EP01403059A EP1225322B1 EP 1225322 B1 EP1225322 B1 EP 1225322B1 EP 01403059 A EP01403059 A EP 01403059A EP 01403059 A EP01403059 A EP 01403059A EP 1225322 B1 EP1225322 B1 EP 1225322B1
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EP
European Patent Office
Prior art keywords
shaft
ring
sleeve
shoes
arrangement according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
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EP01403059A
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German (de)
French (fr)
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EP1225322A1 (en
Inventor
Christophe Emile Galand
Jean-Luc Soupizon
Jean-Bernard Vache
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP1225322A1 publication Critical patent/EP1225322A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants

Definitions

  • the invention relates to a device for centering a tube or a piece inside a hollow turbine shaft in a turbomachine, said tube or piece being secured in rotation to said shaft at its ends, this device comprising a sheath integral with the tube or part and surrounding the latter, an elastic ring interposed between the sleeve and the shaft and having pairs of pads which extend radially outwards, and means for allowing the expansion of the ring after assembly so that the pads bear against the inner wall of the shaft.
  • a tube which allows the venting front and rear speakers of the bearings that support the rotors. This tube allows the evacuation of an oiled air flow.
  • This tube extends over the entire length of the turbine shaft, and has at its ends supports that secure it in rotation to this shaft.
  • This very elongated tube has a relatively thin wall because it transmits no torque. Its moment of transversal inertia is reduced. Under these conditions, if unbalance, even very weak, exist, these imbalances are detrimental to the good behavior of this tube during operation of the turbomachine and can maintain flapping beats of this tube, which can damage, and the adjacent rooms.
  • At least one centering device for coaxially retaining the central region of the tube inside the hollow shaft.
  • FIG. 1 shows an aviation jet engine 1 of X axis which comprises inside the low pressure turbine shaft 2 a tube 3 of X axis.
  • This tube 3 allows the venting of the enclosures front 4 and rear 5 of the front 6 and rear 7 bearings that support the rotors.
  • This tube 3 is rotatably connected at its ends to the low-pressure turbine shaft 2. Between the ends of the tube 3, there are two centering devices 8a, 8b for coaxially retaining portions of the tube 3 inside the tube. tree 2, and thus avoid the bending of the tube 3.
  • the configuration of the current centering devices 8a and 8b is shown in FIGS. 2 and 3.
  • the thin-walled tube 3 comprises a reinforced annular portion 3a, around which is mounted a sleeve 9 which has at one end 9a an external thread 10 and at the other end 9b a conical peripheral wall 11 which diverges in the extension threading 10.
  • a split elastic ring 12 whose inner wall is also conical, is slid by the threaded end 9a on the sleeve 9.
  • a nut 14 having an internal thread adapted to the thread 10, advances the ring 12 on the conical wall 11 This causes the ring 12 to expand.
  • the split elastic ring 12 shown in detail in FIG. 3 has a substantially square section peripheral surface with rounded corners 15 whose curvature is adapted according to the inside diameter of the shaft 2. During the expansion of the ring 12, the corners 15 bear against the inner wall of the shaft 2.
  • the elastic ring 12 thus has four rigid pads of large radial cross section delimited externally by the wedges 15 and connected in pairs by ring sections of smaller radial section.
  • the elastic ring 12 has a lateral slot 16 and behaves like the assembly of two cantilevered beams having their embedding in the zone 17 diametrically opposite the slot 16. Along these beams, the values bending moment and boom are variable, so the support efforts are not the same for all four points of support. As a result, the contact stresses between the elastic ring 12 and the turbine shaft 2 are also different along the supports.
  • the object of the invention is to provide a device for retaining a tube inside a shaft, as mentioned in the introduction, which avoids the marking of the bore of the shaft.
  • the pads comprise thin cylindrical and resilient walls having at rest an outer diameter slightly different from the inner diameter of the hollow shaft and conforming to the inner wall of the shaft after assembly.
  • the radial section of the pads according to the invention in a plane containing the axis of rotation of the turbomachine is significantly reduced compared to that of the pads of the prior art.
  • This arrangement ensures the distribution of radial forces, due to the tightening torque, over a larger area and reduces the contact stresses between the pads and the bore of the turbine shaft.
  • the ring is a split elastic ring and the means for allowing expansion of the ring after assembly comprise a male / female cone system formed on the sleeve and the ring and a nut ensuring by clamping on the sleeve the axial displacement of the ring, its radial expansion and the deformation of the thin walls of the pads.
  • the split ring has a substantially cylindrical inner wall and each pad is connected by its central axial zone to said cylindrical inner wall by means of a radial wall and has a flexible lip on each side. said radial wall.
  • the outer diameter of the pads at rest is greater than the inner diameter of the shaft and decreases during assembly.
  • the split ring has several cylindrical sections alternating with the pads, the ends of each pad being recessed respectively on the two adjacent cylindrical sections.
  • the outer diameter of the pads at rest is less than the inner diameter of the shaft and increases during assembly.
  • each pad has a cylindrical thin wall having at rest an outside diameter less than the inside diameter of the shaft, and at each end of the thin wall, a sector-shaped body, and the bodies are retained axially by two elastic rods to form a ring which, at rest, has an internal diameter smaller than the outer diameter of the sleeve.
  • the sheath comprises a shoulder for axially retaining the bodies on a cylindrical portion of the sheath, and the bodies have on the side of the shoulder a chamfer allowing expansion of the ring and rushes when mounting the ring by tightening a nut on the sleeve.
  • four pads are regularly distributed around the axis of rotation of the turbomachine.
  • the means for allowing expansion of the ring during assembly comprise a male / female cone system formed on the sleeve and the bodies and a nut ensuring by clamping on the sheath the displacement. axial body, radial expansion of bodies and rods, and deformation of the thin walls of the pads.
  • the circumscribed circle of the set of pads has a diameter slightly smaller than the inside diameter of the shaft, to allow the installation of the device in the bore of the turbine shaft before mounting the tube.
  • the tube 3 comprises, as in the prior state, a reinforced annular portion, not shown in FIGS. 4 to 14, about which is mounted a sleeve 9 which has a first threaded end 9a and a second end 9b in the extension of the threaded end 9a for receiving an expandable ring 20.
  • the ring 20 is retained on the sleeve 9 by a nut 14 which has an internal thread cooperating with the thread of the end 9a of the sleeve 9.
  • the ring 20 is interposed between the sleeve 9 and the inner wall 21 of the turbine shaft 2.
  • FIGs 4 to 14 only the inner wall 21 of the turbine shaft 2 is shown for the sake of clarity. This inner wall 21 has a radius E / 2 to the right of the ring 20 after introduction of the centering device into the bore of the turbine shaft 2 and mounting the tube 3.
  • the ring 20 has a slot 22 as in the prior art described in the introduction.
  • the expandable ring 20 has a substantially cylindrical inner wall 23 which, after assembly, surrounds the sheath 9.
  • the inner wall 23 extend, radially outwardly in orthogonal planes intersecting along the axis of rotation X of the turbomachine, four radial walls 24 or more which support at their ends pads 25 wall thin and cylindrical.
  • Each pad 25 has on each side of the radial support wall 24, a flexible lip, respectively 26a and 26b.
  • each pad 25 becomes equal to the radius E / 2 of the turbine shaft.
  • Each pad 25 is therefore in homogeneous support against the inner wall 21 over its entire outer surface.
  • the ring 20 slides on the end 9b of the sleeve 9 and is expanded radially outwards, thanks to a male / female cone system formed at the outer periphery of the end. 9b and the inner periphery of the ring 20.
  • the four pads 25, which come into bearing against the inner wall 21 of the turbine shaft are formed by thin cylindrical walls which, at rest, have an outer radius R2 less than the inner radius E / 2 of the turbine shaft.
  • the radially inner portion of the ring 20 has a plurality of cylindrical sections 27 circumferentially spaced from each other and alternating with the pads 25.
  • each shoe 25 is recessed respectively on two adjacent sections 27.
  • a slot 22 is formed in one of the sections 27.
  • this second variant of the centering device in the turbine shaft is identical to that of the first variant described above.
  • the median zones 28 of the pads flex when one exerts a tightening torque by means of the nut 14 which causes an increase in the radius R2, until the outer radius of the pads is equal to the radius E / 2 of the turbine shaft.
  • the tube 3 is then mounted.
  • the bearing surfaces of the pads 25 against the inner wall 21 of the turbine shaft are considerably increased compared with those of the prior art described in the introduction, in which the pads are rigid non-deformable blocks alternating with connection sections smaller section.
  • the elastic ring 20 is constituted by four identical independent elements 30 assembled by means of two elastic annular rods 31.
  • Each element 30 has in its central region a pad 25 consisting of a cylindrical thin wall whose outer radius R2 is smaller than the radius E / 2 of the turbine shaft.
  • the ends 25a and 25b of each pad 25 are respectively embedded on two bodies 31a and 31b which form the lateral and radially inner portions of an element 30.
  • the blocks 31a, 31b have the shape of a sector of a circle.
  • Each set 30 is thus in the form of a sector that extends over 90 ° at most.
  • the four elements 30 are assembled together by means of two rods 31 which are housed in grooves formed on the outer peripheral wall of the bodies 31a and 31b, one of the grooves being provided near the front face of the ring 20 and the other near its backside.
  • Interstices 32 separate the four elements 30 retained by the rods 31. These interstices 32 widen when the ring 20 is expanded.
  • FIG. 12 shows an alternative embodiment of the mounting of the ring 20, described above, on the sheath 9.
  • the latter comprises a shoulder 33 which extends radially outwards, against which is supported a front face of the ring 20.
  • the ring 20 covers a cylindrical portion 34 of sheath, which has a diameter greater than the outer diameter of the threaded end 9a and greater than the inner diameter of the ring 20 before mounting on the Sleeve 9.
  • the bodies 31a and 31b have, on the side of the shoulder 33, a chamfer 35 which allows the expansion of the ring 20 and rods 31 when the ring rises on the cylindrical portion 34 as a result of the tightening of the nut 14.
  • the circle circumscribing the four pads 25 has a radius smaller than the inner radius E / 2 of the turbine shaft.
  • the median axial zones 28 of the pads 25 will be bent and the outer radius of the pads 25 will be substantially equal to the inner radius E / 2 of the turbine shaft.
  • FIG. 14 shows another alternative embodiment of the mounting of the ring 20 on the sleeve 9.
  • the sleeve 9 and the bodies 31a and 31b comprise a male / female cone system. which allows the expansion of the ring 20 and rods 31 when a tightening torque is applied to the nut 14.
  • a washer 36 can naturally be interposed between the ring 20 and the nut 14 in all the embodiments or embodiments described above.
  • pads 25 on each expandable ring 20 there are provided four pads 25 on each expandable ring 20.
  • the number of pads can obviously be different, and preferably this number is even. What matters most is that these pads are evenly distributed around the axis of rotation X of the turbine.
  • the pads 25 are constituted by thin and deformable cylindrical walls, the bearing surfaces of these pads are relatively high, and the forces are distributed over a large area, without creating prohibitive contact constraints between the centering device. and the bore of the turbine shaft. This avoids markings on the turbine shaft.
  • the second embodiment of the invention allows a better distribution of forces on all the pads, because of the symmetry.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
  • Ultra Sonic Daignosis Equipment (AREA)
  • A Measuring Device Byusing Mechanical Method (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Mutual Connection Of Rods And Tubes (AREA)
  • Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)

Abstract

A device for centering a component positioned inside and rotationally secured at its end to a turbine hollow shaft positioned in a gas turbine engine. The device includes a sheath enclosing and solidly joined to the component, and an elastic ring interposed between the sheath and the shaft. The ring includes a plurality of pairs of opposed shoes extending radially outwardly therefrom and configured to radially expand so as to extend against an inner portion of the shaft. The shoes include thin, elastic cylindrical walls having an external diameter configured slightly less than the internal diameter of the shaft prior to assembly onto the shaft, and arranged to expand to the inner wall of the shaft when assembled thereon.

Description

L'invention concerne un dispositif de centrage d'un tube ou d'une pièce à l'intérieur d'un arbre creux de turbine dans une turbomachine, ce tube ou cette pièce étant solidarisé en rotation audit arbre à ses extrémités, ce dispositif comportant un fourreau solidaire du tube ou de la pièce et entourant ce dernier, un anneau élastique interposé entre le fourreau et l'arbre et présentant des paires de patins qui s'étendent radialement vers l'extérieur, et des moyens pour permettre l'expansion de l'anneau après assemblage afin que les patins soient en appui contre la paroi intérieure de l'arbre.The invention relates to a device for centering a tube or a piece inside a hollow turbine shaft in a turbomachine, said tube or piece being secured in rotation to said shaft at its ends, this device comprising a sheath integral with the tube or part and surrounding the latter, an elastic ring interposed between the sleeve and the shaft and having pairs of pads which extend radially outwards, and means for allowing the expansion of the ring after assembly so that the pads bear against the inner wall of the shaft.

Dans les turbomachines d'aviation, il est prévu coaxialement à l'intérieur de l'arbre central creux, qui relie la turbine basse pression au compresseur basse pression et éventuellement à la soufflante, un tube, qui permet la mise à l'air libre des enceintes avant et arrière des paliers qui supportent les rotors. Ce tube permet l'évacuation d'un débit d'air huilé.In aviation turbomachines, there is provided coaxially inside the hollow central shaft, which connects the low pressure turbine to the low pressure compressor and possibly to the fan, a tube, which allows the venting front and rear speakers of the bearings that support the rotors. This tube allows the evacuation of an oiled air flow.

Ce tube s'étend sur toute la longueur de l'arbre de turbine, et il comporte à ses extrémités des appuis qui le solidarisent en rotation à cet arbre. Ce tube très allongé a une paroi relativement mince, car il ne transmet aucun couple. Son moment d'inertie transversal est donc réduit. Dans ces conditions, si des balourds, même très faibles, existent, ces balourds sont préjudiciables au bon comportement de ce tube lors du fonctionnement de la turbomachine et peuvent entretenir des battements en flexion de ce tube, qui peuvent l'endommager, ainsi que les pièces adjacentes.This tube extends over the entire length of the turbine shaft, and has at its ends supports that secure it in rotation to this shaft. This very elongated tube has a relatively thin wall because it transmits no torque. Its moment of transversal inertia is reduced. Under these conditions, if unbalance, even very weak, exist, these imbalances are detrimental to the good behavior of this tube during operation of the turbomachine and can maintain flapping beats of this tube, which can damage, and the adjacent rooms.

Pour éviter de tels incidents on dispose entre les deux appuis extrêmes du tube au moins un dispositif de centrage pour retenir coaxialement la zone médiane du tube à l'intérieur de l'arbre creux.To avoid such incidents there is disposed between the two extreme supports of the tube at least one centering device for coaxially retaining the central region of the tube inside the hollow shaft.

La figure 1 montre un turboréacteur d'aviation 1 d'axe X qui comporte à l'intérieur de l'arbre de turbine basse pression 2 un tube 3 d'axe X. Ce tube 3 permet la mise à l'air libre des enceintes avant 4 et arrière 5 des paliers avant 6 et arrière 7 qui supportent les rotors. Ce tube 3 est solidarisé en rotation à ses extrémités à l'arbre de turbine basse pression 2. Entre les extrémités du tube 3, il est prévu deux dispositifs de centrage 8a, 8b pour retenir coaxialement des parties du tube 3 à l'intérieur de l'arbre 2, et éviter ainsi la flexion du tube 3. La configuration des dispositifs de centrage 8a et 8b actuels est montrée sur les figures 2 et 3.FIG. 1 shows an aviation jet engine 1 of X axis which comprises inside the low pressure turbine shaft 2 a tube 3 of X axis. This tube 3 allows the venting of the enclosures front 4 and rear 5 of the front 6 and rear 7 bearings that support the rotors. This tube 3 is rotatably connected at its ends to the low-pressure turbine shaft 2. Between the ends of the tube 3, there are two centering devices 8a, 8b for coaxially retaining portions of the tube 3 inside the tube. tree 2, and thus avoid the bending of the tube 3. The configuration of the current centering devices 8a and 8b is shown in FIGS. 2 and 3.

Le tube 3, à paroi mince, comporte une portion annulaire renforcée 3a, autour de laquelle est monté un fourreau 9 qui présente à une extrémité 9a un filetage extérieur 10 et à l'autre extrémité 9b une paroi périphérique conique 11 qui diverge dans le prolongement du filetage 10.The thin-walled tube 3 comprises a reinforced annular portion 3a, around which is mounted a sleeve 9 which has at one end 9a an external thread 10 and at the other end 9b a conical peripheral wall 11 which diverges in the extension threading 10.

Un anneau élastique fendu 12, dont la paroi intérieur est également conique, est glissé par l'extrémité filetée 9a sur le fourreau 9. Un écrou 14 comportant un filetage intérieur adapté au filetage 10, fait progresser l'anneau 12 sur la paroi conique 11. Ce qui provoque l'expansion de l'anneau 12.A split elastic ring 12, whose inner wall is also conical, is slid by the threaded end 9a on the sleeve 9. A nut 14 having an internal thread adapted to the thread 10, advances the ring 12 on the conical wall 11 This causes the ring 12 to expand.

L'anneau élastique fendu 12, montré en détail sur la figure 3, présente une surface périphérique à section sensiblement carrée avec des coins 15 arrondis dont la courbure est adaptée en fonction du diamètre intérieur de l'arbre 2. Lors de l'expansion de l'anneau 12, les coins 15 viennent en appui contre la paroi intérieure de l'arbre 2.The split elastic ring 12, shown in detail in FIG. 3, has a substantially square section peripheral surface with rounded corners 15 whose curvature is adapted according to the inside diameter of the shaft 2. During the expansion of the ring 12, the corners 15 bear against the inner wall of the shaft 2.

L'anneau élastique 12 présente ainsi quatre patins rigides de grande section radiale, délimités extérieurement par les coins 15, et reliés deux à deux par des tronçons d'anneau de plus faible section radiale.The elastic ring 12 thus has four rigid pads of large radial cross section delimited externally by the wedges 15 and connected in pairs by ring sections of smaller radial section.

L'anneau élastique 12 présente une fente latérale 16 et se comporte comme l'ensemble de deux poutres montées en porte-à-faux et ayant leur encastrement dans la zone 17 diamétralement opposée à la fente 16. Le long de ces poutres, les valeurs du moment de flexion et de la flèche sont variables, les efforts d'appui ne sont donc pas les mêmes pour les quatre points d'appui. Il en résulte que les contraintes de contact entre l'anneau élastique 12 et l'arbre de turbine 2 sont aussi différentes le long des appuis.The elastic ring 12 has a lateral slot 16 and behaves like the assembly of two cantilevered beams having their embedding in the zone 17 diametrically opposite the slot 16. Along these beams, the values bending moment and boom are variable, so the support efforts are not the same for all four points of support. As a result, the contact stresses between the elastic ring 12 and the turbine shaft 2 are also different along the supports.

Il arrive que ces valeurs de contraintes soient prohibitives, et alors des marquages ou empreintes peuvent survenir sur l'alésage intérieur de l'arbre de turbine 2, ce qui peut entraîner des conséquences très graves, du fait que cet arbre 2 est soumis à un couple de torsion considérable.It happens that these stress values are prohibitive, and then markings or indentations can occur on the inner bore of the turbine shaft 2, which can lead to very serious consequences, because this shaft 2 is subjected to a considerable torque.

Le but de l'invention est de proposer un dispositif de rétention d'un tube à l'intérieur d'un arbre, tel que mentionné en introduction, qui évite le marquage de l'alésage de l'arbre.The object of the invention is to provide a device for retaining a tube inside a shaft, as mentioned in the introduction, which avoids the marking of the bore of the shaft.

Le but est atteint selon l'invention par le fait que les patins comportent des parois minces cylindriques et élastiques ayant au repos un diamètre extérieur légèrement différent du diamètre intérieur de l'arbre creux et épousant la paroi interne de l'arbre après assemblage.The object is achieved according to the invention in that the pads comprise thin cylindrical and resilient walls having at rest an outer diameter slightly different from the inner diameter of the hollow shaft and conforming to the inner wall of the shaft after assembly.

Ainsi, la section radiale des patins selon l'invention, selon un plan contenant l'axe de rotation de la turbomachine est nettement diminuée par rapport à celle des patins de l'art antérieur. Cette disposition assure la répartition des efforts radiaux, dus au couple de serrage, sur une plus grande surface et réduit les contraintes de contact entre les patins et l'alésage de l'arbre de turbine.Thus, the radial section of the pads according to the invention, in a plane containing the axis of rotation of the turbomachine is significantly reduced compared to that of the pads of the prior art. This arrangement ensures the distribution of radial forces, due to the tightening torque, over a larger area and reduces the contact stresses between the pads and the bore of the turbine shaft.

Selon un premier mode de réalisation de l'invention, l'anneau est un anneau élastique fendu et les moyens pour permettre l'expansion de l'anneau après assemblage comportent un système de cône mâle/femelle formé sur le fourreau et l'anneau et un écrou assurant par serrage sur le fourreau le déplacement axial de l'anneau, son expansion radiale et la déformation des parois minces des patins.According to a first embodiment of the invention, the ring is a split elastic ring and the means for allowing expansion of the ring after assembly comprise a male / female cone system formed on the sleeve and the ring and a nut ensuring by clamping on the sleeve the axial displacement of the ring, its radial expansion and the deformation of the thin walls of the pads.

Selon une première variante du premier mode de réalisation, l'anneau fendu comporte une paroi intérieure sensiblement cylindrique et chaque patin est relié par sa zone axiale médiane à ladite paroi intérieure cylindrique au moyen d'une paroi radiale et présente une lèvre flexible de chaque côté de ladite paroi radiale.According to a first variant of the first embodiment, the split ring has a substantially cylindrical inner wall and each pad is connected by its central axial zone to said cylindrical inner wall by means of a radial wall and has a flexible lip on each side. said radial wall.

Dans cette première variante, le diamètre extérieur des patins au repos est supérieur au diamètre intérieur de l'arbre et décroît lors de l'assemblage.In this first variant, the outer diameter of the pads at rest is greater than the inner diameter of the shaft and decreases during assembly.

Selon une deuxième variante, l'anneau fendu comporte plusieurs tronçons cylindriques alternant avec les patins, les extrémités de chaque patin étant encastrées respectivement sur les deux tronçons cylindriques adjacents.According to a second variant, the split ring has several cylindrical sections alternating with the pads, the ends of each pad being recessed respectively on the two adjacent cylindrical sections.

Dans cette deuxième variante, le diamètre extérieur des patins au repos est inférieur au diamètre intérieur de l'arbre et croit lors de l'assemblage.In this second variant, the outer diameter of the pads at rest is less than the inner diameter of the shaft and increases during assembly.

Selon un deuxième mode de réalisation de l'invention chaque patin comporte une paroi mince cylindrique ayant au repos un diamètre extérieur inférieur au diamètre intérieur de l'arbre, et, à chaque extrémité de la paroi mince, un corps en forme de secteur, et les corps sont retenus axialement par deux joncs élastiques pour former un anneau qui, au repos, a un diamètre intérieur inférieur au diamètre extérieur du fourreau.According to a second embodiment of the invention, each pad has a cylindrical thin wall having at rest an outside diameter less than the inside diameter of the shaft, and at each end of the thin wall, a sector-shaped body, and the bodies are retained axially by two elastic rods to form a ring which, at rest, has an internal diameter smaller than the outer diameter of the sleeve.

Selon une première variante du deuxième mode de réalisation, le fourreau comporte un épaulement pour retenir axialement les corps sur une portion cylindrique de fourreau, et les corps présentent du côté de l'épaulement un chanfrein permettant l'expansion de l'anneau et des joncs lors du montage de l'anneau par serrage d'un écrou sur le fourreau.According to a first variant of the second embodiment, the sheath comprises a shoulder for axially retaining the bodies on a cylindrical portion of the sheath, and the bodies have on the side of the shoulder a chamfer allowing expansion of the ring and rushes when mounting the ring by tightening a nut on the sleeve.

Avantageusement il est prévu quatre patins régulièrement répartis autour de l'axe de rotation de la turbomachine.Advantageously, four pads are regularly distributed around the axis of rotation of the turbomachine.

Selon une autre variante du deuxième mode de réalisation, les moyens pour permettre l'expansion de l'anneau lors du montage comportent un système de cône mâle/femelle formé sur le fourreau et les corps et un écrou assurant par serrage sur le fourreau le déplacement axial des corps, l'expansion radiale des corps et des joncs, et la déformation des parois minces des patins.According to another variant of the second embodiment, the means for allowing expansion of the ring during assembly comprise a male / female cone system formed on the sleeve and the bodies and a nut ensuring by clamping on the sheath the displacement. axial body, radial expansion of bodies and rods, and deformation of the thin walls of the pads.

Selon une autre caractéristique avantageuse de l'invention, au repos, le cercle circonscrit de l'ensemble des patins a un diamètre légèrement inférieur au diamètre intérieur de l'arbre, pour permettre la mise en place du dispositif dans l'alésage de l'arbre de turbine avant le montage du tube.According to another advantageous characteristic of the invention, at rest, the circumscribed circle of the set of pads has a diameter slightly smaller than the inside diameter of the shaft, to allow the installation of the device in the bore of the turbine shaft before mounting the tube.

D'autres avantages et caractéristiques de l'invention ressortiront à la lecture de la description suivante faite à titre d'exemple et en référence aux dessins annexés dans lesquels :

  • la figure 1 est une coupe d'un turboréacteur qui montre la position du dispositif de centrage du tube disposé coaxialement à l'intérieur de l'arbre de turbine basse pression ;
  • la figure 2 est une vue en coupe d'un dispositif de centrage selon l'art antérieur ;
  • la figure 3 est une vue de face de l'anneau élastique fendu selon l'art antérieur ;
  • la figure 4 est une vue frontale de l'anneau élastique fendu selon la première variante du premier mode de réalisation de l' invention ;
  • la figure 5 est une coupe selon un plan radial passant par l'axe de rotation de la turbomachine du dispositif de centrage de l'invention selon une première variante d'un premier mode de réalisation, l'anneau fendu étant coupé selon la ligne V-V de la figure 4 ;
  • La figure 6 montre la configuration d'un patin selon la première variante avant l'assemblage ;
  • la figure 7 montre la configuration d'un patin après assemblage;
  • la figure 8 est une vue frontale d'un anneau élastique fendu selon une deuxième variante du premier mode de réalisation de l'invention ;
  • la figure 9 est une coupe selon un plan axial, passant par l'axe de rotation de la turbomachine, du dispositif de centrage de l'invention selon la deuxième variante de réalisation, l'anneau fendu étant coupé selon la ligne IX-IX de la figure 8 ;
  • la figure 10 montre le rayon extérieur du patin de la figure 8 avant et après assemblage ;
  • la figure 11 est une vue frontale d'un anneau élastique selon un deuxième mode de réalisation de l'invention, cet anneau comportant quatre patins indépendants retenus axialement par deux joncs élastiques ;
  • la figure 12 est une coupe selon un plan axial, passant par l'axe de rotation de la turbomachine, du dispositif de centrage selon le deuxième mode de réalisation à l'état assemblé, l'anneau étant coupé selon la ligne XII-XII de la figure 11;
  • la figure 13 montre en détail la variation du rayon extérieur des patins au cours de l'expansion de l'anneau de la figure 11; et
  • la figure 14 est semblable à la figure 12 et montre une variante de réalisation du système d'expansion de l'anneau.
Other advantages and characteristics of the invention will become apparent on reading the following description given by way of example and with reference to the appended drawings in which:
  • Figure 1 is a section of a turbojet that shows the position of the centering device of the tube disposed coaxially inside the low pressure turbine shaft;
  • Figure 2 is a sectional view of a centering device according to the prior art;
  • Figure 3 is a front view of the split elastic ring according to the prior art;
  • Figure 4 is a front view of the split elastic ring according to the first variant of the first embodiment of the invention;
  • FIG. 5 is a section along a radial plane passing through the axis of rotation of the turbomachine of the centering device of the invention according to a first variant of a first embodiment, the split ring being cut along the line VV. of Figure 4;
  • Figure 6 shows the configuration of a pad according to the first variant before assembly;
  • Figure 7 shows the configuration of a shoe after assembly;
  • Figure 8 is a front view of a split elastic ring according to a second variant of the first embodiment of the invention;
  • FIG. 9 is a section along an axial plane, passing through the axis of rotation of the turbomachine, of the centering device of the invention according to the second variant embodiment, the split ring being cut along line IX-IX of FIG. Figure 8;
  • Figure 10 shows the outer radius of the pad of Figure 8 before and after assembly;
  • FIG. 11 is a front view of an elastic ring according to a second embodiment of the invention, this ring comprising four independent skids retained axially by two elastic rods;
  • FIG. 12 is a section along an axial plane, passing through the axis of rotation of the turbomachine, of the centering device according to the second embodiment in the assembled state, the ring being cut along line XII-XII of FIG. Figure 11;
  • Figure 13 shows in detail the variation of the outer radius of the pads during the expansion of the ring of Figure 11; and
  • Figure 14 is similar to Figure 12 and shows an alternative embodiment of the ring expansion system.

Les figures 1 à 3 ont été commentées dans l'introduction et ne demandent pas d'explications supplémentaires.Figures 1 to 3 have been commented in the introduction and do not require further explanation.

Selon l'invention, le tube 3 comporte, comme dans l'état antérieur, une portion annulaire renforcée, non montrée sur les figures 4 à 14, autour de laquelle est monté un fourreau 9 qui comporte une première extrémité filetée 9a et une deuxième extrémité 9b dans le prolongement de l'extrémité filetée 9a destinée à recevoir un anneau expansible 20. L'anneau 20 est retenu sur le fourreau 9 par un écrou 14 qui comporte un filetage intérieur coopérant avec le filetage de l'extrémité 9a du fourreau 9. L'anneau 20 est interposé entre le fourreau 9 et la paroi interne 21 de l'arbre de turbine 2. Sur les figures 4 à 14 seule la paroi interne 21 de l'arbre de turbine 2 est représentée par souci de clarté. Cette paroi interne 21 a un rayon E/2 au droit de l'anneau 20 après introduction du dispositif de centrage dans l'alésage de l'arbre de turbine 2 et montage du tube 3.According to the invention, the tube 3 comprises, as in the prior state, a reinforced annular portion, not shown in FIGS. 4 to 14, about which is mounted a sleeve 9 which has a first threaded end 9a and a second end 9b in the extension of the threaded end 9a for receiving an expandable ring 20. The ring 20 is retained on the sleeve 9 by a nut 14 which has an internal thread cooperating with the thread of the end 9a of the sleeve 9. The ring 20 is interposed between the sleeve 9 and the inner wall 21 of the turbine shaft 2. In Figures 4 to 14 only the inner wall 21 of the turbine shaft 2 is shown for the sake of clarity. This inner wall 21 has a radius E / 2 to the right of the ring 20 after introduction of the centering device into the bore of the turbine shaft 2 and mounting the tube 3.

Selon un premier mode de réalisation de l'invention, l'anneau 20 présente une fente 22 comme dans l'art antérieur décrit en introduction.According to a first embodiment of the invention, the ring 20 has a slot 22 as in the prior art described in the introduction.

Selon une première variante du premier mode de réalisation de l'invention, représentée sur les figures 4 à 7, l'anneau expansible 20 comporte une paroi intérieure 23 sensiblement cylindrique qui, après montage, entoure le fourreau 9.According to a first variant of the first embodiment of the invention, represented in FIGS. 4 to 7, the expandable ring 20 has a substantially cylindrical inner wall 23 which, after assembly, surrounds the sheath 9.

Autour de la paroi intérieure 23 s'étendent, radialement vers l'extérieur dans des plans orthogonaux se coupant le long de l'axe de rotation X de la turbomachine, quatre parois radiales 24 ou plusieurs qui supportent à leurs extrémités des patins 25 à paroi mince et cylindrique.Around the inner wall 23 extend, radially outwardly in orthogonal planes intersecting along the axis of rotation X of the turbomachine, four radial walls 24 or more which support at their ends pads 25 wall thin and cylindrical.

Chaque patin 25 présente de chaque côté de la paroi radiale 24 de support, une lèvre flexible, respectivement 26a et 26b.Each pad 25 has on each side of the radial support wall 24, a flexible lip, respectively 26a and 26b.

A l'état de repos des patins 25, montré sur la figure 6, le rayon extérieur R2 de leur paroi cylindrique est légèrement supérieur au rayon intérieur E/2 de l'arbre de turbine. Dans cette situation, le diamètre du cercle circonscrit aux quatre patins est supérieur au diamètre intérieur B de l'arbre de turbine.In the rest state of the pads 25, shown in Figure 6, the outer radius R2 of their cylindrical wall is slightly greater than the inner radius E / 2 of the turbine shaft. In this situation, the diameter of the circle circumscribing the four pads is greater than the internal diameter B of the turbine shaft.

Lors de l'assemblage, les extrémités des lèvres 26a et 26b seront fléchies au contact de l'alésage de l'arbre de turbine en serrant l'écrou 14. Dans la configuration assemblée montrée sur la figure 7, le rayon extérieur de la paroi cylindrique de chaque patin 25 devient égal au rayon E/2 de l'arbre de turbine. Chaque patin 25 est donc en appui homogène contre la paroi interne 21 sur toute sa surface extérieure.During assembly, the ends of the lips 26a and 26b will be bent in contact with the bore of the turbine shaft by tightening the nut 14. In the assembled configuration shown in FIG. the outer radius of the cylindrical wall of each pad 25 becomes equal to the radius E / 2 of the turbine shaft. Each pad 25 is therefore in homogeneous support against the inner wall 21 over its entire outer surface.

Lors du serrage de l'écrou 14, l'anneau 20 glisse sur l'extrémité 9b du fourreau 9 et subit un expansion radiale vers l'extérieur, grâce à un système de cône mâle/femelle formé à la périphérie externe de l'extrémité de fourreau 9b et à la périphérie interne de l'anneau 20.When tightening the nut 14, the ring 20 slides on the end 9b of the sleeve 9 and is expanded radially outwards, thanks to a male / female cone system formed at the outer periphery of the end. 9b and the inner periphery of the ring 20.

Pour monter le dispositif de centrage décrit ci-dessus dans l'arbre de turbine, on place l'anneau 20 et l'écrou 14 non serré sur le fourreau 9. On place l'ensemble dans l'arbre de turbine. On exerce un couple de serrage au moyen de l'écrou 14 afin que les zones axiales médianes des patins 25 soient situées à une distance E/2 de l'axe X, ce qui fait fléchir les lèvres 26a et 26b. On monte ensuite le tube 3.To mount the centering device described above in the turbine shaft, is placed the ring 20 and the nut 14 not tightened on the sleeve 9. The set is placed in the turbine shaft. A tightening torque is exerted by means of the nut 14 so that the median axial areas of the pads 25 are located at a distance E / 2 of the X axis, which causes the lips 26a and 26b to bend. The tube 3 is then mounted.

Selon une deuxième variante du premier mode de réalisation de l'invention, montrée sur les figures 8 à 10, qui diffère de la première variante décrite ci-dessus uniquement par la géométrie de l'anneau 20, les quatre patins 25, qui viennent en appui contre la paroi interne 21 de l'arbre de turbine, sont formés par des parois cylindriques minces qui, au repos, ont un rayon extérieur R2 inférieur au rayon intérieur E/2 de l'arbre de turbine.According to a second variant of the first embodiment of the invention, shown in Figures 8 to 10, which differs from the first variant described above solely by the geometry of the ring 20, the four pads 25, which come into bearing against the inner wall 21 of the turbine shaft, are formed by thin cylindrical walls which, at rest, have an outer radius R2 less than the inner radius E / 2 of the turbine shaft.

La partie radialement intérieure de l'anneau 20 comporte plusieurs tronçons cylindriques 27 espacés circonférentiellement l'un de l'autre et alternant avec les patins 25.The radially inner portion of the ring 20 has a plurality of cylindrical sections 27 circumferentially spaced from each other and alternating with the pads 25.

Les extrémités 25a et 25b de chaque patin 25 sont encastrées respectivement sur deux tronçons 27 adjacents. Une fente 22 est ménagée dans l'un des tronçons 27.The ends 25a and 25b of each shoe 25 are recessed respectively on two adjacent sections 27. A slot 22 is formed in one of the sections 27.

L'expansion de cet anneau 20 sur le fourreau 9 par le système à cône et serrage de l'écrou 14 entraîne une augmentation du rayon du cercle circonscrit aux quatre patins 25 à l'état de repos.The expansion of this ring 20 on the sleeve 9 by the cone system and tightening of the nut 14 causes an increase in the radius of the circle circumscribed to the four pads 25 in the state of rest.

Le montage de cette deuxième variante du dispositif de centrage dans l'arbre de turbine est identique à celui de la première variante décrite ci-dessus. Les zones médianes 28 des patins fléchissent lorsqu'on exerce un couple de serrage au moyen de l'écrou 14 ce qui entraîne une augmentation du rayon R2, jusqu' à ce que le rayon extérieur des patins soit égal au rayon E/2 de l'arbre de turbine. On monte ensuite le tube 3.The mounting of this second variant of the centering device in the turbine shaft is identical to that of the first variant described above. The median zones 28 of the pads flex when one exerts a tightening torque by means of the nut 14 which causes an increase in the radius R2, until the outer radius of the pads is equal to the radius E / 2 of the turbine shaft. The tube 3 is then mounted.

Les surfaces d'appui des patins 25 contre la paroi interne 21 de l'arbre de turbine sont considérablement augmentées par rapport à celles de l'art antérieur décrit en introduction, dans lequel les patins sont des blocs rigides indéformables alternant avec des tronçons de raccordement à section plus réduite.The bearing surfaces of the pads 25 against the inner wall 21 of the turbine shaft are considerably increased compared with those of the prior art described in the introduction, in which the pads are rigid non-deformable blocks alternating with connection sections smaller section.

Selon un deuxième mode de réalisation de l'invention, illustré par les figures 11 à 14, l'anneau élastique 20 est constitué par quatre éléments identiques 30 indépendants assemblés au moyen de deux joncs annulaires élastiques 31.According to a second embodiment of the invention, illustrated by FIGS. 11 to 14, the elastic ring 20 is constituted by four identical independent elements 30 assembled by means of two elastic annular rods 31.

Chaque élément 30 comporte dans sa région médiane un patin 25 constitué d'une paroi mince cylindrique dont le rayon extérieur R2 est inférieur au rayon E/2 de l'arbre de turbine. Les extrémités 25a et 25b de chaque patin 25 sont encastrés respectivement sur deux corps 31a et 31b qui forment les parties latérales et radialement intérieures d'un élément 30. Les blocs 31a, 31b ont la forme d'un secteur de cercle.Each element 30 has in its central region a pad 25 consisting of a cylindrical thin wall whose outer radius R2 is smaller than the radius E / 2 of the turbine shaft. The ends 25a and 25b of each pad 25 are respectively embedded on two bodies 31a and 31b which form the lateral and radially inner portions of an element 30. The blocks 31a, 31b have the shape of a sector of a circle.

Chaque ensemble 30 se présente ainsi sous la forme d'un secteur qui s'étend sur 90° au plus.Each set 30 is thus in the form of a sector that extends over 90 ° at most.

Les quatre éléments 30 sont assemblés entre eux au moyen de deux joncs 31 qui logent dans des gorges ménagées sur la paroi périphérique externe des corps 31a et 31b, l'une des gorges étant prévue près de la face avant de l'anneau 20 et l'autre près de sa face arrière.The four elements 30 are assembled together by means of two rods 31 which are housed in grooves formed on the outer peripheral wall of the bodies 31a and 31b, one of the grooves being provided near the front face of the ring 20 and the other near its backside.

Des interstices 32 séparent les quatre éléments 30 retenus par les joncs 31. Ces interstices 32 s'élargissent lorsque l'anneau 20 est expansé.Interstices 32 separate the four elements 30 retained by the rods 31. These interstices 32 widen when the ring 20 is expanded.

La figure 12 montre une variante de réalisation du montage de l'anneau 20, décrit ci-dessus, sur le fourreau 9. Ce dernier comporte un épaulement 33 qui s'étend radialement vers l'extérieur, contre lequel vient appuyer une face frontale de l'anneau 20. L'anneau 20 recouvre une portion cylindrique 34 de fourreau, qui a un diamètre supérieur au diamètre extérieur de l'extrémité filetée 9a et supérieur au diamètre intérieur de l'anneau 20 avant son montage sur le fourreau 9. Les corps 31a et 31b présentent, du côté de l'épaulement 33, un chanfrein 35 qui permet l'expansion de l'anneau 20 et des joncs 31 lorsque l'anneau monte sur la partie cylindrique 34 par suite du serrage de l'écrou 14.FIG. 12 shows an alternative embodiment of the mounting of the ring 20, described above, on the sheath 9. The latter comprises a shoulder 33 which extends radially outwards, against which is supported a front face of the ring 20. The ring 20 covers a cylindrical portion 34 of sheath, which has a diameter greater than the outer diameter of the threaded end 9a and greater than the inner diameter of the ring 20 before mounting on the Sleeve 9. The bodies 31a and 31b have, on the side of the shoulder 33, a chamfer 35 which allows the expansion of the ring 20 and rods 31 when the ring rises on the cylindrical portion 34 as a result of the tightening of the nut 14.

Dans cette configuration de repos, le cercle circonscrit aux quatre patins 25 a un rayon inférieur au rayon intérieur E/2 de l'arbre de turbine. Lorsque le tube sera en place dans l'arbre de turbine, les zones axiales médianes 28 des patins 25 seront fléchies et le rayon extérieur des patins 25 sera sensiblement égal au rayon intérieur E/2 de l'arbre de turbine.In this rest configuration, the circle circumscribing the four pads 25 has a radius smaller than the inner radius E / 2 of the turbine shaft. When the tube is in place in the turbine shaft, the median axial zones 28 of the pads 25 will be bent and the outer radius of the pads 25 will be substantially equal to the inner radius E / 2 of the turbine shaft.

La figure 14 montre une autre variante de réalisation du montage de l'anneau 20 sur le fourreau 9. Comme dans le premier mode de réalisation de l'invention, le fourreau 9 et les corps 31a et 31b comportent un système de cône mâle/femelle qui permet l'expansion de l'anneau 20 et des joncs 31 lorsqu'on exerce un couple de serrage sur l'écrou 14.FIG. 14 shows another alternative embodiment of the mounting of the ring 20 on the sleeve 9. As in the first embodiment of the invention, the sleeve 9 and the bodies 31a and 31b comprise a male / female cone system. which allows the expansion of the ring 20 and rods 31 when a tightening torque is applied to the nut 14.

Une rondelle 36 peut naturellement être interposée entre l'anneau 20 et l'écrou 14 dans tous les modes ou variantes de réalisation décrits ci-dessus.A washer 36 can naturally be interposed between the ring 20 and the nut 14 in all the embodiments or embodiments described above.

Dans la description faite ci-dessus, il est prévu quatre patins 25 sur chaque anneau expansible 20. Le nombre de patins peut évidemment être différent, et de préférence ce nombre est pair. Ce qui importe surtout, c'est que ces patins soient régulièrement répartis autour de l'axe de rotation X de la turbine.In the description above, there are provided four pads 25 on each expandable ring 20. The number of pads can obviously be different, and preferably this number is even. What matters most is that these pads are evenly distributed around the axis of rotation X of the turbine.

Du fait que les patins 25 sont constitués par des parois cylindriques minces et déformables, les surfaces d'appui de ces patins sont relativement élevées, et les efforts sont répartis sur une grande surface, sans créer des contraintes de contacts prohibitifs entre le dispositif de centrage et l'alésage de l'arbre de turbine. Ceci évite des marquages sur l'arbre de turbine.Because the pads 25 are constituted by thin and deformable cylindrical walls, the bearing surfaces of these pads are relatively high, and the forces are distributed over a large area, without creating prohibitive contact constraints between the centering device. and the bore of the turbine shaft. This avoids markings on the turbine shaft.

En outre, le deuxième mode de réalisation de l'invention permet une meilleure répartition des efforts sur tous les patins, du fait de la symétrie.In addition, the second embodiment of the invention allows a better distribution of forces on all the pads, because of the symmetry.

Claims (11)

  1. Turbomachine shaft arrangement comprising a hollow shaft (2), a tube (3) or a component positioned inside the shaft (2) and rotationally secured to the latter at its ends, a device for centring the tube (3) or the component within the shaft, this device comprising a sleeve (9) secured to the said tube (3) or to the said component and surrounding the latter, an elastic ring (20) interposed between the sleeve (9) and the shaft (2) and exhibiting pairs of shoes which extend radially outwards, and means for allowing the ring (20) to be expanded after the device has been assembled so that the said shoes bear against the interior wall of the shaft, characterized in that the shoes are formed of elastic thin walls (25), the diameter of the circle circumscribing the shoes being, at rest, slightly different from the inside diameter of the hollow shaft (2), the thin walls hugging the internal wall (21) of the shaft (2) after assembly.
  2. Shaft arrangement according to Claim 1, characterized in that the ring (20) is a split elastic ring and the means for allowing the ring (20) to expand after assembly comprise a male/female taper system formed on the sleeve (9) and the ring (20) and a nut (14) which, by being tightened onto the sleeve (9), causes the axial displacement of the ring (20), its radial expansion, and the deformation of the thin walls of the shoes.
  3. Shaft arrangement according to Claim 2, characterized in that the ring (20) comprises a more or less cylindrical interior wall (23) and each shoe is connected by its central axial region to the said cylindrical interior wall (23) via a radial wall (24) and exhibits a flexible lip (26a, 26b) on each side of the said radial wall (24).
  4. Shaft arrangement according to Claim 3, characterized in that the outside diameter of the shoes (25) at rest is greater than the inside diameter of the shaft (2) and decreases at the time of assembly.
  5. Shaft arrangement according to Claim 2, characterized in that the ring (20) comprises several cylindrical sections (27) alternating with the shoes (25), the ends (25a, 25b) of each shoe (25) being set respectively into the two adjacent cylindrical sections (27).
  6. Shaft arrangement according to Claim 5, characterized in that the outside diameter of the shoes (25) at rest is smaller than the inside diameter of the shaft (2) and increases at the time of assembly.
  7. Shaft arrangement according to Claim 1, characterized in that each shoe (25) comprises a cylindrical thin wall having, at rest, an outside diameter smaller than the inside diameter of the shaft (2) and, at each end of the said thin wall, a body (31a, 31b) in the shape of a sector, and in that the said bodies (31a, 31b) are axially retained by two elastic snap rings (31) to form a ring (20) which, at rest, has an inside diameter smaller than the outside diameter of the sleeve (9).
  8. Shaft arrangement according to Claim 7, characterized in that the sleeve (9) has a shoulder (33) for axially retaining the bodies (31a, 31b) on a cylindrical portion (34) of the sleeve (9), the said bodies (31a, 31b) having, on the same side as the shoulder (33), a chamfer (35) allowing the ring (20) and the snap rings (31) to expand as the ring (20) is being mounted through the tightening of a nut (14) onto the sleeve (9).
  9. Shaft arrangement according to Claim 7, characterized in that the means for allowing the ring (20) to expand during the mounting comprise a male/female taper system formed on the sleeve (9) and the bodies (31a, 31b) and a nut (14) which, by being tightened onto the sleeve (9), causes the axial movement of the bodies (31a, 31b), the radial expansion of the bodies (31a, 31b) and of the snap rings (31) and the deformation of the thin walls of the shoes (25).
  10. Shaft arrangement according to one of Claims 1 to 9, characterized in that, at rest, the circle circumscribing the collection of shoes (25) has a diameter slightly smaller than the inside diameter of the shaft (2).
  11. Shaft arrangement according to any one of Claims 1 to 10, characterized in that it comprises four shoes (25) uniformly distributed about the axis of rotation (X) of the turbomachine.
EP01403059A 2000-11-30 2001-11-29 Apparatus to centre a tube in a turbine shaft Expired - Lifetime EP1225322B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0015473A FR2817289B1 (en) 2000-11-30 2000-11-30 DEVICE FOR CENTERING A TUBE IN A TURBINE SHAFT
FR0015473 2000-11-30

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EP1225322A1 EP1225322A1 (en) 2002-07-24
EP1225322B1 true EP1225322B1 (en) 2006-02-01

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US (1) US7004725B2 (en)
EP (1) EP1225322B1 (en)
JP (1) JP4043944B2 (en)
CN (1) CN1250868C (en)
AT (1) ATE317060T1 (en)
CA (1) CA2430285C (en)
DE (1) DE60116987T2 (en)
ES (1) ES2253342T3 (en)
FR (1) FR2817289B1 (en)
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WO (1) WO2002044538A2 (en)

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CN1250868C (en) 2006-04-12
WO2002044538A3 (en) 2002-08-01
US7004725B2 (en) 2006-02-28
US20040025494A1 (en) 2004-02-12
FR2817289B1 (en) 2003-01-31
ATE317060T1 (en) 2006-02-15
CA2430285A1 (en) 2002-06-06
JP2004514841A (en) 2004-05-20
FR2817289A1 (en) 2002-05-31
CA2430285C (en) 2008-10-07
EP1225322A1 (en) 2002-07-24
ES2253342T3 (en) 2006-06-01
DE60116987T2 (en) 2006-09-21
CN1395649A (en) 2003-02-05
RU2249702C2 (en) 2005-04-10
DE60116987D1 (en) 2006-04-13
JP4043944B2 (en) 2008-02-06
WO2002044538A2 (en) 2002-06-06

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